GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 285 AIRFOIL (goe285-il) Reynolds number: 500,000 Max Cl/Cd: 89.29 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe285-il-500000.txt Download as CSV file: xf-goe285-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 285 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3762 0.08495 0.08259 -0.0364 1.0000 0.0413
-8.500 -0.3802 0.08201 0.07969 -0.0368 1.0000 0.0422
-8.250 -0.3984 0.07855 0.07630 -0.0369 1.0000 0.0434
-8.000 -0.4482 0.02408 0.02090 -0.0725 0.9820 0.0393
-7.750 -0.4664 0.03615 0.03280 -0.0698 0.9846 0.0385
-7.500 -0.4538 0.02814 0.02414 -0.0724 0.9780 0.0370
-7.250 -0.4313 0.02220 0.01737 -0.0741 0.9733 0.0362
-7.000 -0.3976 0.01989 0.01468 -0.0761 0.9709 0.0363
-6.750 -0.3697 0.01845 0.01301 -0.0764 0.9634 0.0366
-6.500 -0.3370 0.01720 0.01157 -0.0775 0.9587 0.0369
-6.250 -0.3083 0.01621 0.01042 -0.0777 0.9501 0.0373
-6.000 -0.2766 0.01537 0.00944 -0.0783 0.9430 0.0379
-5.750 -0.2488 0.01473 0.00868 -0.0782 0.9318 0.0384
-5.500 -0.2202 0.01412 0.00796 -0.0781 0.9208 0.0388
-5.250 -0.1927 0.01337 0.00709 -0.0778 0.9087 0.0392
-5.000 -0.1665 0.01259 0.00624 -0.0773 0.8958 0.0398
-4.750 -0.1403 0.01209 0.00569 -0.0768 0.8826 0.0405
-4.500 -0.1138 0.01171 0.00526 -0.0763 0.8695 0.0412
-4.250 -0.0872 0.01139 0.00486 -0.0758 0.8563 0.0421
-4.000 -0.0608 0.01110 0.00449 -0.0752 0.8424 0.0431
-3.750 -0.0342 0.01085 0.00416 -0.0747 0.8285 0.0442
-3.500 -0.0077 0.01054 0.00380 -0.0742 0.8153 0.0458
-3.250 0.0191 0.01030 0.00354 -0.0738 0.8028 0.0478
-3.000 0.0461 0.01013 0.00331 -0.0734 0.7896 0.0501
-2.750 0.0729 0.00994 0.00307 -0.0729 0.7753 0.0537
-2.500 0.0999 0.00977 0.00290 -0.0726 0.7604 0.0606
-2.250 0.1271 0.00963 0.00279 -0.0722 0.7452 0.0757
-2.000 0.1544 0.00956 0.00268 -0.0719 0.7296 0.0889
-1.750 0.1814 0.00948 0.00259 -0.0716 0.7131 0.0990
-1.500 0.2086 0.00943 0.00249 -0.0712 0.6967 0.1068
-1.250 0.2359 0.00940 0.00242 -0.0710 0.6818 0.1144
-1.000 0.2631 0.00936 0.00234 -0.0707 0.6677 0.1231
-0.750 0.2903 0.00934 0.00229 -0.0704 0.6540 0.1337
-0.250 0.3444 0.00919 0.00219 -0.0699 0.6267 0.1747
0.000 0.3710 0.00900 0.00215 -0.0696 0.6134 0.2331
0.250 0.3941 0.00824 0.00216 -0.0691 0.6002 0.4909
0.500 0.4079 0.00717 0.00229 -0.0657 0.5873 0.8669
0.750 0.4571 0.00727 0.00242 -0.0696 0.5684 0.9776
1.000 0.5106 0.00744 0.00245 -0.0751 0.5453 0.9955
1.250 0.5483 0.00760 0.00245 -0.0772 0.5222 1.0000
1.500 0.5726 0.00773 0.00247 -0.0764 0.5009 1.0000
1.750 0.5967 0.00790 0.00250 -0.0756 0.4809 1.0000
2.000 0.6208 0.00807 0.00256 -0.0747 0.4634 1.0000
2.250 0.6449 0.00825 0.00263 -0.0739 0.4482 1.0000
2.500 0.6690 0.00843 0.00272 -0.0731 0.4346 1.0000
2.750 0.6929 0.00863 0.00283 -0.0723 0.4217 1.0000
3.000 0.7175 0.00879 0.00293 -0.0715 0.4093 1.0000
3.250 0.7419 0.00896 0.00304 -0.0708 0.3972 1.0000
3.500 0.7661 0.00916 0.00316 -0.0700 0.3846 1.0000
3.750 0.7901 0.00936 0.00329 -0.0692 0.3709 1.0000
4.250 0.8383 0.00980 0.00357 -0.0677 0.3369 1.0000
4.500 0.8623 0.01005 0.00372 -0.0669 0.3192 1.0000
4.750 0.8862 0.01031 0.00389 -0.0662 0.3056 1.0000
5.000 0.9108 0.01054 0.00407 -0.0655 0.2954 1.0000
5.250 0.9352 0.01079 0.00428 -0.0649 0.2867 1.0000
5.500 0.9595 0.01105 0.00449 -0.0643 0.2784 1.0000
5.750 0.9842 0.01129 0.00470 -0.0637 0.2720 1.0000
6.000 1.0090 0.01152 0.00492 -0.0631 0.2659 1.0000
6.250 1.0329 0.01182 0.00517 -0.0625 0.2607 1.0000
6.500 1.0582 0.01202 0.00540 -0.0620 0.2568 1.0000
6.750 1.0831 0.01224 0.00564 -0.0615 0.2518 1.0000
7.000 1.1069 0.01253 0.00590 -0.0609 0.2463 1.0000
7.250 1.1316 0.01277 0.00616 -0.0603 0.2418 1.0000
7.500 1.1566 0.01298 0.00640 -0.0599 0.2368 1.0000
7.750 1.1802 0.01327 0.00668 -0.0592 0.2314 1.0000
8.000 1.2045 0.01351 0.00695 -0.0587 0.2257 1.0000
8.250 1.2286 0.01376 0.00721 -0.0581 0.2178 1.0000
8.500 1.2521 0.01405 0.00750 -0.0575 0.2104 1.0000
8.750 1.2752 0.01435 0.00779 -0.0568 0.1997 1.0000
9.000 1.2982 0.01467 0.00807 -0.0561 0.1813 1.0000
9.250 1.3066 0.01609 0.00899 -0.0534 0.1095 1.0000
9.500 1.3184 0.01720 0.00995 -0.0511 0.0822 1.0000
9.750 1.3286 0.01835 0.01089 -0.0487 0.0539 1.0000
10.000 1.3415 0.01917 0.01167 -0.0465 0.0467 1.0000
10.250 1.3542 0.01991 0.01243 -0.0442 0.0439 1.0000
10.500 1.3653 0.02077 0.01332 -0.0419 0.0417 1.0000
10.750 1.3780 0.02154 0.01416 -0.0399 0.0405 1.0000
11.000 1.3899 0.02238 0.01507 -0.0379 0.0394 1.0000
11.250 1.4001 0.02335 0.01612 -0.0358 0.0383 1.0000
11.500 1.4078 0.02453 0.01735 -0.0337 0.0372 1.0000
11.750 1.4121 0.02600 0.01889 -0.0314 0.0363 1.0000
12.000 1.4124 0.02787 0.02085 -0.0292 0.0355 1.0000
12.250 1.4203 0.02928 0.02235 -0.0278 0.0350 1.0000
12.500 1.4267 0.03090 0.02406 -0.0266 0.0345 1.0000
12.750 1.4314 0.03274 0.02599 -0.0254 0.0338 1.0000
13.000 1.4346 0.03481 0.02816 -0.0245 0.0332 1.0000
13.250 1.4360 0.03715 0.03058 -0.0237 0.0326 1.0000
13.500 1.4358 0.03977 0.03329 -0.0231 0.0321 1.0000
13.750 1.4337 0.04272 0.03632 -0.0227 0.0316 1.0000
14.000 1.4290 0.04604 0.03973 -0.0225 0.0312 1.0000
14.250 1.4214 0.04976 0.04354 -0.0225 0.0308 1.0000
14.500 1.4112 0.05377 0.04763 -0.0224 0.0304 1.0000
14.750 1.4089 0.05704 0.05100 -0.0225 0.0301 1.0000
15.000 1.4092 0.06013 0.05419 -0.0229 0.0297 1.0000
15.250 1.4083 0.06340 0.05756 -0.0233 0.0293 1.0000
15.500 1.4067 0.06680 0.06105 -0.0238 0.0289 1.0000
15.750 1.4047 0.07030 0.06464 -0.0244 0.0285 1.0000
16.000 1.4028 0.07383 0.06825 -0.0251 0.0280 1.0000
16.250 1.4008 0.07734 0.07184 -0.0257 0.0277 1.0000
16.500 1.3991 0.08083 0.07540 -0.0264 0.0273 1.0000
16.750 1.3981 0.08421 0.07882 -0.0270 0.0269 1.0000
17.000 1.3977 0.08741 0.08206 -0.0275 0.0265 1.0000
17.250 1.3996 0.08986 0.08451 -0.0273 0.0260 1.0000
17.500 1.4015 0.09231 0.08700 -0.0269 0.0255 1.0000
17.750 1.3995 0.09624 0.09105 -0.0283 0.0252 1.0000
18.000 1.3977 0.10010 0.09503 -0.0297 0.0249 1.0000
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